US20140363622A1 - Flexible ceramic matrix composite seal - Google Patents
Flexible ceramic matrix composite seal Download PDFInfo
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- US20140363622A1 US20140363622A1 US14/140,663 US201314140663A US2014363622A1 US 20140363622 A1 US20140363622 A1 US 20140363622A1 US 201314140663 A US201314140663 A US 201314140663A US 2014363622 A1 US2014363622 A1 US 2014363622A1
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- fiber assembly
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/30—Woven fabric [i.e., woven strand or strip material]
- Y10T442/3472—Woven fabric including an additional woven fabric layer
- Y10T442/3528—Three or more fabric layers
Definitions
- the present disclosure relates generally to ceramic matrix composite seals, and more specifically to a ceramic matrix composite seal including a ceramic matrix and a number of ceramic fiber fabrics embedded in the ceramic matrix to form the ceramic matrix composite seal with a desired geometry.
- Strip seals also called feather seals, may be used to eliminate leakage flow between two components arranged adjacently to one another. This may be achieved by the two components having groove recesses in edge faces that lie substantially opposite and adjacent one another.
- the strip seal seals the gap between the two components by being at least partially received into the groove recesses of the adjacently fitted components to span the gap between the components.
- the grooved recesses of fitted components often do not perfectly align due to, for example, manufacturing tolerances or thermal expansion.
- a ceramic matrix composite seal may include a ceramic matrix, a first fiber assembly, and a second fiber assembly.
- the first fiber assembly is embedded in the ceramic matrix.
- the first fiber assembly includes a first top fabric and a second top fabric.
- the second fiber assembly is embedded in the ceramic matrix.
- the second fiber assembly includes a first bottom fabric and a second bottom fabric. The second fiber assembly is spaced apart from and opposite the first fiber assembly.
- the second top fabric of the first fiber assembly is coupled to the first bottom fabric of the second fiber assembly by the ceramic matrix.
- the first top fabric and the second top fabric determine the shape of the first fiber assembly.
- the first bottom fabric and the second bottom fabric determine the shape of the second fiber assembly.
- the second fiber assembly is about flat.
- the first fiber assembly includes a depression along a length of the first fiber assembly at a center of the first fiber assembly. The depression extends toward the second fiber assembly.
- the first fiber assembly includes a first depression along a length of the first fiber assembly at a center of the first fiber assembly, the first depression extending toward the second fiber assembly, and the second fiber assembly includes a second depression along a length of the second fiber assembly at a center of the second fiber assembly, and the second depression extends toward the first fiber assembly.
- the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the first top fabric may lie in a first plane.
- the third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- the second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second top fabric may lie in the second plane.
- the third portion of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- the first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first, second, and third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- the second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first, second, and third portions of the second bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the first top fabric may lie in a first plane.
- the third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- the second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second top fabric may lie in the second plane.
- the third portion of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- the first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and the second portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- the third portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- the second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second bottom fabric may lie in the fifth plane.
- the third portion of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane.
- the ceramic matrix composite seal may include reinforcement structure extending through the third portions of the first top fabric, second top fabric, first bottom fabric, and the second bottom fabric in a direction about perpendicular to the first plane.
- the first top fabric may include a first portion, second portions, and a third portion coupled between the first and the second portions.
- the first and second portions of the first top fabric may lie in a first plane.
- the third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- the second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and third portions of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- the second portion of the second top fabric may lie in the second plane.
- the first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and the third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- the second portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- the second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane.
- the third portion of the second bottom fabric may lie in the fifth plane.
- the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and third portions of the first top fabric may lie in a second plane.
- the second portion of the first top fabric may lie in a first plane spaced apart from, parallel with, and above the second plane.
- the second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and third portions of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- the second portion of the second top fabric may lie in the second plane.
- the first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the second and the third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- the first portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- the second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane.
- the third portion of the second bottom fabric may lie in the fifth plane.
- the first top fabric may be curved extending downwardly toward the second top fabric in a concave shape.
- the second top fabric may be about flat.
- the first bottom fabric may be about flat.
- the second bottom fabric may be curved extending upwardly toward the first bottom fabric in a concave shape.
- the first top fabric may be curved extending downwardly toward the second top fabric in a concave shape.
- the second top fabric may be curved extending downwardly toward the first bottom fabric in a concave shape.
- the first bottom fabric may be curved extending upwardly toward the second top fabric in a concave shape.
- the second bottom fabric may be curved extending upwardly toward the first bottom fabric in a concave shape.
- the first and second top fabrics may have about the same shape.
- the first and second bottom fabrics may have about the same shape.
- the first top fabric may include a first portion, second portions, and a third portion coupled between the first and the second portions.
- the first and second portions of the first top fabric may be curved and extend upwardly in a convex shape.
- the third portion of the first top fabric may be curved and extend downwardly in a concave shape.
- the second top fabric may be about flat.
- the first bottom fabric may be about flat.
- the second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions.
- the first and second portions of the second bottom fabric may be curved and extend downwardly in a convex shape.
- the third portion of the second bottom fabric may be curved and extend upwardly in a concave shape.
- the ceramic matrix composite seal may include a reinforcement structure extending through the third portion of the first top fabric to the third portion of the second bottom fabric.
- a slot may be formed in a surface of the ceramic matrix composite seal between the first and the second fiber assemblies.
- the slot may extend along a length of the ceramic matrix composite seal.
- FIG. 1 is a front elevation view of an annular strip seal in accordance with the present disclosure
- FIG. 2 is a front elevation view of a liner strip seal in accordance with the present disclosure
- FIG. 3 is cross-sectional diagrammatic view of the strip seal of FIG. 1 or 2 taken along line 3 - 3 ;
- FIG. 4 is a cross-sectional diagrammatic view of an exemplary sealing application using the strip seal of FIG. 2 ;
- FIG. 5 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the strip seal includes a number of ceramic fiber fabrics spaced apart from each other, the ceramic fiber fabrics having a desired geometry to give the strip seal a desired geometry;
- FIG. 6 is a cross-sectional diagrammatic view of the ceramic fiber fabrics of FIG. 5 embedded in a ceramic matrix to form a top fabric assembly and a bottom fabric assembly;
- FIG. 7A is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the top fabric assembly and the bottom fabric assembly may be coupled together with the ceramic matrix to form slots between the top fabric assembly and the bottom fabric assembly;
- FIG. 7B is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the top fabric assembly and the bottom fabric assembly may be coupled together with the ceramic matrix such that no slots are formed between the top fabric assembly and the bottom fabric assembly;
- FIG. 8 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a first ceramic fiber fabric geometry
- FIG. 9 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a second ceramic fiber fabric geometry, the strip seal having fiber reinforcement;
- FIG. 10 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a third ceramic fiber fabric geometry;
- FIG. 11 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a fourth ceramic fiber fabric geometry;
- FIG. 12 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a fifth ceramic fiber fabric geometry;
- FIG. 13 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a sixth ceramic fiber fabric geometry.
- FIG. 14 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with seventh ceramic fiber fabric geometry, the strip seal having fiber reinforcement.
- a strip seal 10 in accordance with the present disclosure is shown, for example, in FIG. 1 .
- the strip seal 10 provides compliance to allow the strip seal 10 to be pre-loaded. Additionally, the strip seal 10 may be used in applications with a broader range of groove or gap tolerances.
- the strip seal 10 has a constant cross section. In some embodiments, the strip seal 10 has a varying cross section. In some embodiments, the strip seal 10 includes features that allow a number strip seals 10 to be used within a single assembly. In some embodiments, for example, a number of strip seals 10 are assembled end to end. In some embodiments, for example, a number of strip seals 10 are stacked together to achieve a desired effect. In some embodiments, the strip seal 10 is formed into a continuous hoop, as shown in FIG. 1 , or a split hoop for sealing requirements on cylinders. In some embodiments, for example, the strip seal 10 is formed into a substantially linear ribbon as shown in FIG. 2 . In some embodiments, the strip seal 10 is formed into other polygonal shapes.
- the strip seal 10 may be made from a number of different materials.
- the strip seal 10 is formed from at least one of carbon, silicon carbide, alumina, aluminosilicate or other carbide, nitride, boride or glass fibers.
- the strip seal 10 includes a reinforcement structure 20 .
- the reinforcement structure 20 is a laminate and includes multi-directional reinforcements, for example, fabric, chopped fiber mat, or uni-directional layers.
- the reinforcement structure 20 is locally stitched, woven, or otherwise reinforced to increase mechanical integrity.
- the reinforcement structure 20 is entirely stitched, woven, or otherwise reinforced to maximize mechanical integrity.
- the strip seal 10 includes a matrix material 12 .
- the matrix material 12 may be, for example, silicon, silicon carbide, carbon, boron carbide, alumina, aluminosilicate or any other desirable ceramic including combinations.
- the strip seal 10 is made of a combination of fibers and/or matrices as required by the design to optimize performance and cost.
- the strip seal 10 includes a coating 14 for protection from the operational environment.
- the coating 14 is thin.
- the strip seal 10 includes no coating 14 .
- the strip seal 10 may be configured to adjust the level of the preload applied to the strip seal 10 , seal maximum deflection, seal dynamic behavior, and seal stiffness.
- the strip seal 10 is flexible and deforms plastically.
- the shape of the strip seal 10 and the process used to form the strip seal 10 gives the strip seal 10 flexibility.
- the strip seal 10 may be formed to have one of a variety of cross-sections.
- a first embodiment of the strip seal 10 has a first cross-section is shown in FIGS. 1-8 .
- the strip seal 10 is formed using a number of layers to give the strip seal 10 shape and flexibility.
- the strip seal 10 is formed from ceramic matrix composite 70 .
- the ceramic matrix composite 70 includes a ceramic matrix 72 and a number of ceramic fiber fabrics 74 embedded in the ceramic matrix 72 as shown in FIGS. 7A and 7B .
- the number of ceramic fiber fabrics 74 may be embedded in the ceramic matrix 72 by a variety of methods.
- the ceramic fiber fabrics 74 may be embedded in the ceramic matrix 72 by chemical vapor infiltration (CVI) or polymer infiltration. Any number of ceramic fiber fabrics 74 may be embedded in the ceramic matrix 72 in a given process.
- CVI chemical vapor infiltration
- all of the ceramic fiber fabrics 74 are embedded in the ceramic matrix 72 in one process. In some embodiments, the ceramic fiber fabrics 74 are embedded in the ceramic matrix 72 one at a time. Additional ceramic fiber fabrics 74 impart more flexibility into the strip seal 10 than one ceramic fiber fabric 74 with an equivalent size of the additional ceramic fiber fabrics 74 .
- the ceramic matrix 72 composite may be one or more of a variety of materials.
- the ceramic matrix 72 may be Silicon Carbide (SiC), alumina, and/or Boron Carbide.
- Each of the ceramic fiber fabrics 74 may be at least one of a number of different types of ceramic fiber fabrics.
- the ceramic fiber fabrics 74 may be chopped fiber, fiber tows, woven tows, or woven tows with fiber reinforcement.
- the ceramic fiber fabrics 74 may be one or more of a variety of materials.
- the ceramic fiber fabrics 74 may be Hi-Nicalon, alumina, aluminosilicate, and/or Carbon.
- the strip seal 10 includes four ceramic fiber fabrics 74 as shown in FIG. 5 .
- the ceramic fiber fabrics 74 are formed to have a desired front shape as seen in a cross-sectional view as shown in FIG. 5 .
- the ceramic fiber fabrics 74 are also formed to have a desired top shape as seen in a plan view as shown in FIGS. 1 and 2 .
- the front shape of ceramic fiber fabrics 74 may be formed to give the strip seal 10 a variable amount of flexibility and to control the expansion direction of the strip seal 10 .
- the strip seal 10 includes a top fabric assembly 78 and a bottom fabric assembly 80 as shown in FIG. 5 .
- the top fabric assembly 78 includes a first top fabric 82 and a second top fabric 84 spaced apart from the first top fabric 82 .
- the second top fabric 84 may be spaced apart from the first top fabric 82 by any distance required to give the strip seal 10 a desired thickness and/or flexibility.
- a depression 90 is formed in the first and second top fabrics 82 , 84 . The depression 90 extends along the length of the strip seal 10 .
- the boottom fabric assembly 80 includes a first bottom fabric 92 and a second bottom fabric 94 spaced apart from first bottom fabric 92 .
- the second bottom fabric 94 may be spaced apart from the first bottom fabric 92 by any distance required to give the strip seal 10 a desired thickness and/or flexibility.
- the first and second bottom fabrics 92 , 94 are about flat.
- the strip seal 10 is better at compressive loads applied vertically rather than horizontally because the bottom fabric assembly 80 is about flat.
- the fabric assemblies 78 , 80 that have the ceramic fiber fabrics 74 that are about flat do not deform well when a load is parallel to the flat ceramic fiber fabrics 74 .
- the strip seals 10 with the all non-flat ceramic fiber fabrics 74 perform better than the flat ceramic fiber fabrics 74 under either or both vertical and horizontal loads.
- the top fabric assembly 78 is embedded in the ceramic matrix 72 to form the top ceramic matrix composite assembly 98 .
- the bottom fabric assembly 80 is embedded in the ceramic matrix 72 to form the bottom ceramic matrix composite assembly 100 .
- the top and bottom fabric assemblies 78 , 80 are embedded into the ceramic matrix 72 in the same process.
- the top and bottom fabric assemblies 78 , 80 are embedded into the ceramic matrix 72 in different processes.
- the ceramic matrix 72 is formed between and permeates the first top fabric 82 and the second top fabric 84 to form the top ceramic matrix composite assembly 98 as shown in FIG. 6 . Likewise, the ceramic matrix 72 is formed between and permeates the first bottom fabric 92 and the second bottom fabric 94 to form the bottom ceramic matrix composite assembly 100 as shown in FIG. 6 .
- the top ceramic matrix composite assembly 98 is spaced apart from the bottom ceramic matrix composite assembly 100 by a variable distance to give the strip seal 10 a desired seal height 42 as shown in FIG. 6 .
- the top and bottom ceramic matrix composite assemblies 98 , 100 are coupled together by the ceramic matrix 72 to form the strip seal 10 .
- the strip seal 10 is formed in one process.
- the seal slots 48 are formed in the ceramic matrix 72 between the top and bottom ceramic matrix composite assemblies 98 , 100 as shown in FIG. 7A . In some embodiments, no slots are formed in the ceramic matrix 72 and the space between the top and bottom ceramic matrix assemblies 98 , 100 is entirely filled by the ceramic matrix 72 as shown in FIG. 7B .
- the strip seal 10 is coated with a coating 14 .
- the coating 14 may be applied to any one or more surfaces of the strip seal 10 .
- the coating 14 may have any desirable thickness.
- Each ceramic fiber fabric 74 may be formed into a desired shape.
- the ceramic fiber fabrics 74 include a number of portions having different shapes and positions to give the strip seal 10 a desired shape.
- the first top fabric 82 includes a first portion 110 , a second portion 114 , and a third portion 112 coupled between the first and second portions 110 , 114 .
- the first and second portions 110 , 114 lie in a first plane.
- the third portion 112 lies in a second plane spaced apart from, parallel with, and below the first plane.
- the second top fabric 84 includes a first portion 116 , a second portion 120 , and a third portion 118 coupled between the first and second portions 116 , 120 .
- the first and second portions 116 , 120 lie in the second plane.
- the third portion 118 lies in a third plane spaced apart from, parallel with, and below the second plane.
- the first bottom fabric 92 includes a first portion 122 , a second portion 126 , and a third portion 128 coupled between the first and second portions 122 , 126 .
- the first, second, and third portions 122 , 126 , 124 lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- the second bottom fabric 94 includes a first portion 128 , a second portion 132 , and a third portion 130 coupled between the first and second portions 128 , 132 .
- the first, second, and third portions 128 , 132 , 130 lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- the strip seal 10 includes an upper surface 30 , a lower surface 32 spaced apart from and opposite the upper surface 30 , a first side wall 34 , and a second side wall 36 spaced apart from and opposite the first side wall 34 .
- the upper surface 30 is spaced apart from the lower surface 32 by a seal height 42 .
- the seal height 42 is equal to a seal thickness 44 .
- the first and second side walls 34 , 36 are each formed to define a seal slot 48 extending the length of the strip seal 10 .
- the seal slots 48 allow the strip seal 10 to deform.
- the seal slots 48 allow the top fabric assembly 78 and the bottom fabric assembly 80 to depress toward each other, compressing the size of the strip seal 10 .
- the strip seal 10 stores potential energy. As such, when the strip seal 10 is no longer compressed, the strip seal 10 expands towards its uncompressed shape.
- the seal slots 48 may be any desired shape. In the illustrative embodiment, the seal slots 48 are C shaped. In some embodiments, the seal slots 48 are U shaped. In some embodiments, the seal slot 48 included in the first side wall 34 has a different shape than the seal slot 48 included in the second side wall 36 .
- the seal slots 48 have a seal-slot height 50 as shown in FIG. 3 .
- the seal-slot height may be a variety of magnitudes. In the illustrative embodiment, the seal-slot height 50 is about 0.015 inches when the strip seal 10 is uncompressed.
- the component 16 A, 16 B have component slots 18 , 24 , respectively, configured to receive a portion of the strip seal 10 .
- a first component 16 A includes first component slot 18 configured to receive a first portion 22 of strip seal 10 and a second component 16 B includes the second component slot 24 configured to receive a second portion 26 of strip seal 10 .
- the component slots 18 , 24 extend through the components 16 A, 16 B. In some embodiments, the component slots 18 , 24 extends partially through the components 16 A, 16 B.
- the component slots 18 , 24 have a component-slot height 56 .
- the component-slot height 56 is about equal to the seal height 42 .
- the component-slot height 56 is less than the seal height 42 , such that the strip seal 10 is compressed and/or pre-loaded when assembled in the component slots 18 , 24 .
- the strip seal 10 is inserted into the component slots 18 , 24 and couples to the component 16 A to 16 B.
- the component 16 A may additionally be coupled to the component 16 B by one or more fasteners, for example, a bolt or screw.
- the strip seal 10 and the component slots 18 , 24 are sized such that the strip seal 10 contacts the components 16 to create a seal between the strip seal 10 and the components 16 as well as a seal between the components 16 A and 16 B.
- the components 16 are exposed to high temperatures. The high temperatures cause the components 16 to expand. As the components 16 expand, the component slots 18 , 24 expand.
- the strip seal 10 may not expand proportionally with the component slots 18 , 24 . As such, when the component slots 18 , 24 expand, the strip seal 10 may loose contact with the components 16 and may partially or entirely loose its sealing ability.
- Sizing the component-slot height 56 smaller than the seal height 42 can overcome the loss of contact when the components 16 and the strip seal 10 are exposed to high temperatures.
- the strip seal 10 is preloaded and/or forced into the smaller component-slot height 56 .
- the compression of the strip seal 10 by the components 16 results in contact between the strip seal 10 and the components 16 to produce an acceptable seal.
- the components 16 apply less force to the strip seal 10 .
- the strip seal 10 expands towards its pre-compression seal height 42 as less force is applied to the strip seal 10 .
- the strip seal 10 remains in contact with the components 16 because the strip seal 10 expands as the component slots 18 , 24 expand.
- the strip seal 10 maintains an acceptable seal as the components 16 and the strip seal 10 are heated.
- the component slots 18 , 24 contract and compress the strip seal 10 .
- the strip seal 10 is designed to experience a predetermined number of cycles of expanding and contracting without failing.
- the component slots 18 , 24 may extend into the components 16 by a variety of depths. In some embodiments, the component slots 18 , 24 extend into the components 16 such that the side walls 34 , 36 are proximate or contacting the components 16 as shown in component 16 B of FIG. 4 . In some embodiments, the component slots 18 , 24 extend into the components 16 such that the side walls 34 , 36 are spaced apart from the components 16 as shown in 16 A of FIG. 4 .
- FIGS. 8-14 are cross-sectional views of embodiments of the strip seal 10 .
- Each FIG. 8-14 show an embodiment of the strip seal 10 having different desired geometries to give the strip seal 10 a desired geometry and flexibility and to assert pressure in a desired direction.
- FIGS. 8-14 show only the ceramic fiber fabrics 74 of the strip seal 10 .
- the ceramic fiber fabrics 74 in FIGS. 8-14 may be embedded in the ceramic matrix 72 such that a slot is formed in either or both sides of the strip seal 10 between the top and bottom ceramic matrix composite assemblies 98 , 100 .
- FIG. 8 is a cross-sectional view the strip seal 10 of FIGS. 1-7B .
- FIGS. 9 and 14 show embodiments of the strip seal 10 that include the reinforcement structure 20 .
- a Hi-Nicalon ceramic fiber fabric is constructed at 30% fiber volume using an angle interlock 3D architecture.
- the ceramic fiber fabric is woven to the geometry in FIG. 8 and processed with a chemical vapor infiltration (CVI) Silicon Carbide (SiC) matrix to leave about a 0.015 inch gap between the top ceramic matrix composite assembly 98 and the bottom ceramic matrix composite assembly 100 .
- CVI chemical vapor infiltration
- SiC Silicon Carbide
- the seal is designed to be preloaded by about 0.002 to 0.005 inches allowing about 0.010 inches for movement during operation.
- the seal is designed so that the stresses at max deflection will tolerate 10 10 cycles.
- the seal is used to join a set of 36 high-pressure turbine seal segments in a commercial aircraft turbine engine.
- An alumina fiber ceramic fiber fabric is constructed from a laminate with aluminosilicate fiber reinforcement in the center as shown in FIG. 12 .
- the ceramic fiber fabric is rigidized using an alumina matrix.
- the seal is designed to be preloaded by about 0.010 to 0.015 inches, allowing about 0.015 inches for movement during operation.
- the seal is designed so that the stresses at max deflection will tolerate 10 10 cycles with only 20% softening through the life.
- the seal is used to join adjacent sections of exhaust for a commercial aircraft turbine engine
- An AS4 carbon fiber ceramic fiber fabric is constructed at 38% fiber volume using an angle interlock 3D architecture.
- the ceramic fiber fabric is woven to the geometry in FIG. 14 and processed with a chemical vapor infiltration (CVI) Silicon Carbide (SiC)/Boron Carbide matrix to leave about a 0.075 inch gap between the top and bottom ceramic matrix composite assemblies.
- CVI chemical vapor infiltration
- SiC Silicon Carbide
- Boron Carbide matrix to leave about a 0.075 inch gap between the top and bottom ceramic matrix composite assemblies.
- the seal is designed to be preloaded by about 0.010 to 0.015 inches vertically, thereby applying horizontal pressure to create additional sealing surfaces.
- the seal is designed so that the stresses at max deflection will tolerate 10 5 cycles.
- the seal is used to seal the outlet of a combustor in a short life turbine engine.
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Abstract
Description
- This application claims priority to and the benefit of U.S. Provisional Patent Application No. 61/792,920, filed 15 Mar. 2013, the disclosure of which is now incorporated herein by reference.
- The present disclosure relates generally to ceramic matrix composite seals, and more specifically to a ceramic matrix composite seal including a ceramic matrix and a number of ceramic fiber fabrics embedded in the ceramic matrix to form the ceramic matrix composite seal with a desired geometry.
- Economical and environmental concerns, for example, improving efficiency and reducing emissions, are driving an increasing demand for higher gas turbine operating temperatures. The temperature capability of hot section components in gas turbine engines is currently one limitation to improving efficiency and emissions of many gas turbine engines. Improvements in cooling, materials, and coatings may be able to achieve higher inlet temperatures. Therefore, interest in high temperature materials, such as, for example, ceramic-based materials is growing.
- One hot section component includes a strip seal. Strip seals, also called feather seals, may be used to eliminate leakage flow between two components arranged adjacently to one another. This may be achieved by the two components having groove recesses in edge faces that lie substantially opposite and adjacent one another. The strip seal seals the gap between the two components by being at least partially received into the groove recesses of the adjacently fitted components to span the gap between the components. The grooved recesses of fitted components often do not perfectly align due to, for example, manufacturing tolerances or thermal expansion.
- The present application discloses one or more of the features recited in the appended claims and/or the following features which, alone or in any combination, may comprise patentable subject matter.
- A ceramic matrix composite seal may include a ceramic matrix, a first fiber assembly, and a second fiber assembly. The first fiber assembly is embedded in the ceramic matrix. The first fiber assembly includes a first top fabric and a second top fabric. The second fiber assembly is embedded in the ceramic matrix. The second fiber assembly includes a first bottom fabric and a second bottom fabric. The second fiber assembly is spaced apart from and opposite the first fiber assembly.
- The second top fabric of the first fiber assembly is coupled to the first bottom fabric of the second fiber assembly by the ceramic matrix. The first top fabric and the second top fabric determine the shape of the first fiber assembly. The first bottom fabric and the second bottom fabric determine the shape of the second fiber assembly.
- In some embodiments, the second fiber assembly is about flat. The first fiber assembly includes a depression along a length of the first fiber assembly at a center of the first fiber assembly. The depression extends toward the second fiber assembly.
- In some embodiments, the first fiber assembly includes a first depression along a length of the first fiber assembly at a center of the first fiber assembly, the first depression extending toward the second fiber assembly, and the second fiber assembly includes a second depression along a length of the second fiber assembly at a center of the second fiber assembly, and the second depression extends toward the first fiber assembly.
- In some embodiments, the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the first top fabric may lie in a first plane. The third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- The second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second top fabric may lie in the second plane. The third portion of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- The first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first, second, and third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane.
- The second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first, second, and third portions of the second bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- In some embodiments, the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the first top fabric may lie in a first plane. The third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- The second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second top fabric may lie in the second plane. The third portion of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane.
- The first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and the second portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane. The third portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- The second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second bottom fabric may lie in the fifth plane. The third portion of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane. In some embodiments, the ceramic matrix composite seal may include reinforcement structure extending through the third portions of the first top fabric, second top fabric, first bottom fabric, and the second bottom fabric in a direction about perpendicular to the first plane.
- In some embodiments, the first top fabric may include a first portion, second portions, and a third portion coupled between the first and the second portions. The first and second portions of the first top fabric may lie in a first plane. The third portion of the first top fabric may lie in a second plane spaced apart from, parallel with, and below the first plane.
- The second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and third portions of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane. The second portion of the second top fabric may lie in the second plane.
- The first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and the third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane. The second portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- The second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane. The third portion of the second bottom fabric may lie in the fifth plane.
- In some embodiments, the first top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and third portions of the first top fabric may lie in a second plane. The second portion of the first top fabric may lie in a first plane spaced apart from, parallel with, and above the second plane.
- The second top fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and third portions of the second top fabric may lie in a third plane spaced apart from, parallel with, and below the second plane. The second portion of the second top fabric may lie in the second plane.
- The first bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The second and the third portions of the first bottom fabric may lie in a fourth plane spaced apart from, parallel with, and below the third plane. The first portion of the first bottom fabric may lie in a fifth plane spaced apart from, parallel with, and below the fourth plane.
- The second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second bottom fabric may lie in a sixth plane spaced apart from, parallel with, and below the fifth plane. The third portion of the second bottom fabric may lie in the fifth plane.
- In some embodiments, the first top fabric may be curved extending downwardly toward the second top fabric in a concave shape. The second top fabric may be about flat. The first bottom fabric may be about flat. The second bottom fabric may be curved extending upwardly toward the first bottom fabric in a concave shape.
- In some embodiments, the first top fabric may be curved extending downwardly toward the second top fabric in a concave shape. The second top fabric may be curved extending downwardly toward the first bottom fabric in a concave shape. The first bottom fabric may be curved extending upwardly toward the second top fabric in a concave shape. The second bottom fabric may be curved extending upwardly toward the first bottom fabric in a concave shape.
- In some embodiments, the first and second top fabrics may have about the same shape. The first and second bottom fabrics may have about the same shape.
- In some embodiments, the first top fabric may include a first portion, second portions, and a third portion coupled between the first and the second portions. The first and second portions of the first top fabric may be curved and extend upwardly in a convex shape. The third portion of the first top fabric may be curved and extend downwardly in a concave shape. The second top fabric may be about flat. The first bottom fabric may be about flat. The second bottom fabric may include a first portion, a second portion, and a third portion coupled between the first and the second portions. The first and second portions of the second bottom fabric may be curved and extend downwardly in a convex shape. The third portion of the second bottom fabric may be curved and extend upwardly in a concave shape.
- In some embodiments, the ceramic matrix composite seal may include a reinforcement structure extending through the third portion of the first top fabric to the third portion of the second bottom fabric.
- In some embodiments, a slot may be formed in a surface of the ceramic matrix composite seal between the first and the second fiber assemblies. The slot may extend along a length of the ceramic matrix composite seal.
- These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
-
FIG. 1 is a front elevation view of an annular strip seal in accordance with the present disclosure; -
FIG. 2 is a front elevation view of a liner strip seal in accordance with the present disclosure; -
FIG. 3 is cross-sectional diagrammatic view of the strip seal ofFIG. 1 or 2 taken along line 3-3; -
FIG. 4 is a cross-sectional diagrammatic view of an exemplary sealing application using the strip seal ofFIG. 2 ; -
FIG. 5 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the strip seal includes a number of ceramic fiber fabrics spaced apart from each other, the ceramic fiber fabrics having a desired geometry to give the strip seal a desired geometry; -
FIG. 6 is a cross-sectional diagrammatic view of the ceramic fiber fabrics ofFIG. 5 embedded in a ceramic matrix to form a top fabric assembly and a bottom fabric assembly; -
FIG. 7A is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the top fabric assembly and the bottom fabric assembly may be coupled together with the ceramic matrix to form slots between the top fabric assembly and the bottom fabric assembly; -
FIG. 7B is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure showing that the top fabric assembly and the bottom fabric assembly may be coupled together with the ceramic matrix such that no slots are formed between the top fabric assembly and the bottom fabric assembly; -
FIG. 8 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a first ceramic fiber fabric geometry; -
FIG. 9 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a second ceramic fiber fabric geometry, the strip seal having fiber reinforcement; -
FIG. 10 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a third ceramic fiber fabric geometry; -
FIG. 11 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a fourth ceramic fiber fabric geometry; -
FIG. 12 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a fifth ceramic fiber fabric geometry; -
FIG. 13 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with a sixth ceramic fiber fabric geometry; and -
FIG. 14 is a cross-sectional diagrammatic view of another embodiment of a strip seal in accordance with the present disclosure with seventh ceramic fiber fabric geometry, the strip seal having fiber reinforcement. - For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same.
- A
strip seal 10 in accordance with the present disclosure is shown, for example, inFIG. 1 . Thestrip seal 10 provides compliance to allow thestrip seal 10 to be pre-loaded. Additionally, thestrip seal 10 may be used in applications with a broader range of groove or gap tolerances. - In some embodiments, the
strip seal 10 has a constant cross section. In some embodiments, thestrip seal 10 has a varying cross section. In some embodiments, thestrip seal 10 includes features that allow a number strip seals 10 to be used within a single assembly. In some embodiments, for example, a number of strip seals 10 are assembled end to end. In some embodiments, for example, a number of strip seals 10 are stacked together to achieve a desired effect. In some embodiments, thestrip seal 10 is formed into a continuous hoop, as shown inFIG. 1 , or a split hoop for sealing requirements on cylinders. In some embodiments, for example, thestrip seal 10 is formed into a substantially linear ribbon as shown inFIG. 2 . In some embodiments, thestrip seal 10 is formed into other polygonal shapes. - The
strip seal 10 may be made from a number of different materials. In some embodiments, thestrip seal 10 is formed from at least one of carbon, silicon carbide, alumina, aluminosilicate or other carbide, nitride, boride or glass fibers. In some embodiments, thestrip seal 10 includes areinforcement structure 20. In some embodiments, thereinforcement structure 20 is a laminate and includes multi-directional reinforcements, for example, fabric, chopped fiber mat, or uni-directional layers. In some embodiments, thereinforcement structure 20 is locally stitched, woven, or otherwise reinforced to increase mechanical integrity. In some embodiments, thereinforcement structure 20 is entirely stitched, woven, or otherwise reinforced to maximize mechanical integrity. - The
strip seal 10 includes a matrix material 12. The matrix material 12 may be, for example, silicon, silicon carbide, carbon, boron carbide, alumina, aluminosilicate or any other desirable ceramic including combinations. In some embodiments, thestrip seal 10 is made of a combination of fibers and/or matrices as required by the design to optimize performance and cost. In some embodiments, thestrip seal 10 includes acoating 14 for protection from the operational environment. In some embodiments, thecoating 14 is thin. In some embodiments, thestrip seal 10 includes nocoating 14. Thestrip seal 10 may be configured to adjust the level of the preload applied to thestrip seal 10, seal maximum deflection, seal dynamic behavior, and seal stiffness. - The
strip seal 10 is flexible and deforms plastically. The shape of thestrip seal 10 and the process used to form thestrip seal 10 gives thestrip seal 10 flexibility. Thestrip seal 10 may be formed to have one of a variety of cross-sections. A first embodiment of thestrip seal 10 has a first cross-section is shown inFIGS. 1-8 . - The
strip seal 10 is formed using a number of layers to give thestrip seal 10 shape and flexibility. Thestrip seal 10 is formed fromceramic matrix composite 70. Theceramic matrix composite 70 includes aceramic matrix 72 and a number ofceramic fiber fabrics 74 embedded in theceramic matrix 72 as shown inFIGS. 7A and 7B . The number ofceramic fiber fabrics 74 may be embedded in theceramic matrix 72 by a variety of methods. For example, theceramic fiber fabrics 74 may be embedded in theceramic matrix 72 by chemical vapor infiltration (CVI) or polymer infiltration. Any number ofceramic fiber fabrics 74 may be embedded in theceramic matrix 72 in a given process. - In some embodiments, for example, all of the
ceramic fiber fabrics 74 are embedded in theceramic matrix 72 in one process. In some embodiments, theceramic fiber fabrics 74 are embedded in theceramic matrix 72 one at a time. Additionalceramic fiber fabrics 74 impart more flexibility into thestrip seal 10 than oneceramic fiber fabric 74 with an equivalent size of the additionalceramic fiber fabrics 74. - The
ceramic matrix 72 composite may be one or more of a variety of materials. For example, theceramic matrix 72 may be Silicon Carbide (SiC), alumina, and/or Boron Carbide. Each of theceramic fiber fabrics 74 may be at least one of a number of different types of ceramic fiber fabrics. For example, theceramic fiber fabrics 74 may be chopped fiber, fiber tows, woven tows, or woven tows with fiber reinforcement. Theceramic fiber fabrics 74 may be one or more of a variety of materials. For example, theceramic fiber fabrics 74 may be Hi-Nicalon, alumina, aluminosilicate, and/or Carbon. - In the illustrative embodiment, the
strip seal 10 includes fourceramic fiber fabrics 74 as shown inFIG. 5 . Theceramic fiber fabrics 74 are formed to have a desired front shape as seen in a cross-sectional view as shown inFIG. 5 . Theceramic fiber fabrics 74 are also formed to have a desired top shape as seen in a plan view as shown inFIGS. 1 and 2 . As disclosed in more detail below, the front shape ofceramic fiber fabrics 74 may be formed to give the strip seal 10 a variable amount of flexibility and to control the expansion direction of thestrip seal 10. - The
strip seal 10 includes atop fabric assembly 78 and abottom fabric assembly 80 as shown inFIG. 5 . Thetop fabric assembly 78 includes a firsttop fabric 82 and a secondtop fabric 84 spaced apart from the firsttop fabric 82. The secondtop fabric 84 may be spaced apart from the firsttop fabric 82 by any distance required to give the strip seal 10 a desired thickness and/or flexibility. In the illustrative embodiment, adepression 90 is formed in the first and secondtop fabrics depression 90 extends along the length of thestrip seal 10. - The
boottom fabric assembly 80 includes afirst bottom fabric 92 and asecond bottom fabric 94 spaced apart fromfirst bottom fabric 92. Thesecond bottom fabric 94 may be spaced apart from thefirst bottom fabric 92 by any distance required to give the strip seal 10 a desired thickness and/or flexibility. In the illustrative embodiment, the first and secondbottom fabrics - In the illustrative embodiment, the
strip seal 10 is better at compressive loads applied vertically rather than horizontally because thebottom fabric assembly 80 is about flat. Thefabric assemblies ceramic fiber fabrics 74 that are about flat do not deform well when a load is parallel to the flatceramic fiber fabrics 74. As such, the strip seals 10 with the all non-flatceramic fiber fabrics 74 perform better than the flatceramic fiber fabrics 74 under either or both vertical and horizontal loads. - The
top fabric assembly 78 is embedded in theceramic matrix 72 to form the top ceramic matrixcomposite assembly 98. Thebottom fabric assembly 80 is embedded in theceramic matrix 72 to form the bottom ceramic matrixcomposite assembly 100. In some embodiments, the top andbottom fabric assemblies ceramic matrix 72 in the same process. In some embodiments, the top andbottom fabric assemblies ceramic matrix 72 in different processes. - The
ceramic matrix 72 is formed between and permeates the firsttop fabric 82 and the secondtop fabric 84 to form the top ceramic matrixcomposite assembly 98 as shown inFIG. 6 . Likewise, theceramic matrix 72 is formed between and permeates thefirst bottom fabric 92 and thesecond bottom fabric 94 to form the bottom ceramic matrixcomposite assembly 100 as shown inFIG. 6 . - The top ceramic matrix
composite assembly 98 is spaced apart from the bottom ceramic matrixcomposite assembly 100 by a variable distance to give the strip seal 10 a desiredseal height 42 as shown inFIG. 6 . The top and bottom ceramicmatrix composite assemblies ceramic matrix 72 to form thestrip seal 10. In some embodiments, thestrip seal 10 is formed in one process. - In some embodiments, the
seal slots 48 are formed in theceramic matrix 72 between the top and bottom ceramicmatrix composite assemblies FIG. 7A . In some embodiments, no slots are formed in theceramic matrix 72 and the space between the top and bottomceramic matrix assemblies ceramic matrix 72 as shown inFIG. 7B . - In some embodiments, the
strip seal 10 is coated with acoating 14. Thecoating 14 may be applied to any one or more surfaces of thestrip seal 10. Thecoating 14 may have any desirable thickness. - Each
ceramic fiber fabric 74 may be formed into a desired shape. Theceramic fiber fabrics 74 include a number of portions having different shapes and positions to give the strip seal 10 a desired shape. Referring toFIG. 8 , the firsttop fabric 82 includes afirst portion 110, asecond portion 114, and athird portion 112 coupled between the first andsecond portions second portions third portion 112 lies in a second plane spaced apart from, parallel with, and below the first plane. - The second
top fabric 84 includes afirst portion 116, asecond portion 120, and athird portion 118 coupled between the first andsecond portions second portions third portion 118 lies in a third plane spaced apart from, parallel with, and below the second plane. - The
first bottom fabric 92 includes afirst portion 122, asecond portion 126, and athird portion 128 coupled between the first andsecond portions third portions - The
second bottom fabric 94 includes afirst portion 128, asecond portion 132, and athird portion 130 coupled between the first andsecond portions third portions - Referring to
FIGS. 3 and 4 , thestrip seal 10 includes anupper surface 30, alower surface 32 spaced apart from and opposite theupper surface 30, afirst side wall 34, and asecond side wall 36 spaced apart from and opposite thefirst side wall 34. Theupper surface 30 is spaced apart from thelower surface 32 by aseal height 42. When thestrip seal 10 is uncompressed, theseal height 42 is equal to aseal thickness 44. - The
upper surface 30 includes adepression 90 such that theupper surface 30 forms avalley 54. In the illustrative embodiment, theupper surface 30 includes obtuse angles that form thevalley 54. In some embodiments, theupper surface 30 includes right or acute angles that form thevalley 54. In some embodiments, theupper surface 30 is curved to form thevalley 54. - The first and
second side walls seal slot 48 extending the length of thestrip seal 10. Theseal slots 48 allow thestrip seal 10 to deform. Theseal slots 48 allow thetop fabric assembly 78 and thebottom fabric assembly 80 to depress toward each other, compressing the size of thestrip seal 10. As thestrip seal 10 compresses, thestrip seal 10 stores potential energy. As such, when thestrip seal 10 is no longer compressed, thestrip seal 10 expands towards its uncompressed shape. - The
seal slots 48 may be any desired shape. In the illustrative embodiment, theseal slots 48 are C shaped. In some embodiments, theseal slots 48 are U shaped. In some embodiments, theseal slot 48 included in thefirst side wall 34 has a different shape than theseal slot 48 included in thesecond side wall 36. Theseal slots 48 have a seal-slot height 50 as shown inFIG. 3 . The seal-slot height may be a variety of magnitudes. In the illustrative embodiment, the seal-slot height 50 is about 0.015 inches when thestrip seal 10 is uncompressed. - The
strip seal 10 is formed to have a desired cross-section such that thestrip seal 10 may be assembled with a number of components 16 having mating cross-sections. The components 16 may be one or more of a variety of components 16. In the illustrative embodiment, the components 16 are gas turbine engine components 16 configured to be exposed to high temperatures. In the illustrative embodiment, thestrip seal 10 is shown assembled with afirst component 16A and asecond component 16B. In some embodiments, thestrip seal 10 is assembled with additional components. - As shown in
FIG. 4 , thecomponent component slots 18, 24, respectively, configured to receive a portion of thestrip seal 10. In the illustrative embodiment, afirst component 16A includesfirst component slot 18 configured to receive afirst portion 22 ofstrip seal 10 and asecond component 16B includes the second component slot 24 configured to receive asecond portion 26 ofstrip seal 10. In some embodiments, thecomponent slots 18, 24 extend through thecomponents component slots 18, 24 extends partially through thecomponents - The
component slots 18, 24 have a component-slot height 56. In some embodiments, the component-slot height 56 is about equal to theseal height 42. In some embodiments, the component-slot height 56 is less than theseal height 42, such that thestrip seal 10 is compressed and/or pre-loaded when assembled in thecomponent slots 18, 24. Thestrip seal 10 is inserted into thecomponent slots 18, 24 and couples to thecomponent 16A to 16B. Thecomponent 16A may additionally be coupled to thecomponent 16B by one or more fasteners, for example, a bolt or screw. - When the component-
slot height 56 is less than theseal height 42, theseal slots 48 compress and the seal-slot height 50 is reduced. Preload in thestrip seal 10 reduces and/or eliminates movement and wear of thestrip seal 10. Thestrip seal 10 is flexible and deforms plastically when compressed. In the illustrative embodiment, theseal slots 48 are sized such that when thestrip seal 10 is compressed, the top fabric assembly and thebottom fabric assembly strip seal 10 is thus designed to have infinite life in terms of compression cycles because the top fabric assembly and thebottom fabric assembly - The
strip seal 10 and thecomponent slots 18, 24 are sized such that thestrip seal 10 contacts the components 16 to create a seal between thestrip seal 10 and the components 16 as well as a seal between thecomponents component slots 18, 24 expand. Thestrip seal 10 may not expand proportionally with thecomponent slots 18, 24. As such, when thecomponent slots 18, 24 expand, thestrip seal 10 may loose contact with the components 16 and may partially or entirely loose its sealing ability. - Sizing the component-
slot height 56 smaller than theseal height 42 can overcome the loss of contact when the components 16 and thestrip seal 10 are exposed to high temperatures. Thestrip seal 10 is preloaded and/or forced into the smaller component-slot height 56. When the components 16 are cool, the compression of thestrip seal 10 by the components 16 results in contact between thestrip seal 10 and the components 16 to produce an acceptable seal. As the components 16 are heated and thecomponent slots 18, 24 expand, the components 16 apply less force to thestrip seal 10. Thestrip seal 10 expands towards itspre-compression seal height 42 as less force is applied to thestrip seal 10. Thestrip seal 10 remains in contact with the components 16 because thestrip seal 10 expands as thecomponent slots 18, 24 expand. As such, thestrip seal 10 maintains an acceptable seal as the components 16 and thestrip seal 10 are heated. When the components 16 and thestrip seal 10 cool, thecomponent slots 18, 24 contract and compress thestrip seal 10. Thestrip seal 10 is designed to experience a predetermined number of cycles of expanding and contracting without failing. - The
component slots 18, 24 may extend into the components 16 by a variety of depths. In some embodiments, thecomponent slots 18, 24 extend into the components 16 such that theside walls component 16B ofFIG. 4 . In some embodiments, thecomponent slots 18, 24 extend into the components 16 such that theside walls FIG. 4 . -
FIGS. 8-14 are cross-sectional views of embodiments of thestrip seal 10. EachFIG. 8-14 show an embodiment of thestrip seal 10 having different desired geometries to give the strip seal 10 a desired geometry and flexibility and to assert pressure in a desired direction.FIGS. 8-14 show only theceramic fiber fabrics 74 of thestrip seal 10. In some embodiments, theceramic fiber fabrics 74 inFIGS. 8-14 may be embedded in theceramic matrix 72 such that a slot is formed in either or both sides of thestrip seal 10 between the top and bottom ceramicmatrix composite assemblies FIG. 8 is a cross-sectional view thestrip seal 10 ofFIGS. 1-7B .FIGS. 9 and 14 show embodiments of thestrip seal 10 that include thereinforcement structure 20. - A Hi-Nicalon ceramic fiber fabric is constructed at 30% fiber volume using an angle interlock 3D architecture. The ceramic fiber fabric is woven to the geometry in
FIG. 8 and processed with a chemical vapor infiltration (CVI) Silicon Carbide (SiC) matrix to leave about a 0.015 inch gap between the top ceramic matrixcomposite assembly 98 and the bottom ceramic matrixcomposite assembly 100. - The seal is designed to be preloaded by about 0.002 to 0.005 inches allowing about 0.010 inches for movement during operation. The seal is designed so that the stresses at max deflection will tolerate 1010 cycles. The seal is used to join a set of 36 high-pressure turbine seal segments in a commercial aircraft turbine engine.
- An alumina fiber ceramic fiber fabric is constructed from a laminate with aluminosilicate fiber reinforcement in the center as shown in
FIG. 12 . The ceramic fiber fabric is rigidized using an alumina matrix. The seal is designed to be preloaded by about 0.010 to 0.015 inches, allowing about 0.015 inches for movement during operation. The seal is designed so that the stresses at max deflection will tolerate 1010 cycles with only 20% softening through the life. The seal is used to join adjacent sections of exhaust for a commercial aircraft turbine engine - An AS4 carbon fiber ceramic fiber fabric is constructed at 38% fiber volume using an angle interlock 3D architecture. The ceramic fiber fabric is woven to the geometry in
FIG. 14 and processed with a chemical vapor infiltration (CVI) Silicon Carbide (SiC)/Boron Carbide matrix to leave about a 0.075 inch gap between the top and bottom ceramic matrix composite assemblies. - The seal is designed to be preloaded by about 0.010 to 0.015 inches vertically, thereby applying horizontal pressure to create additional sealing surfaces. The seal is designed so that the stresses at max deflection will tolerate 105 cycles. The seal is used to seal the outlet of a combustor in a short life turbine engine.
- While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
Claims (15)
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Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3061603A1 (en) * | 2015-02-27 | 2016-08-31 | General Electric Company | Cmc laminate structure fabricated using chemical vapor infiltration (cvi) |
US9464535B2 (en) | 2013-05-27 | 2016-10-11 | Kabushiki Kaisha Toshiba | Stationary part sealing structure |
US20170306779A1 (en) * | 2016-04-25 | 2017-10-26 | United Technologies Corporation | Creep resistant axial ring seal |
US20180266261A1 (en) * | 2017-02-27 | 2018-09-20 | Rolls-Royce North American Technologies Inc. | Ceramic seal component for gas turbine engine and process of making the same |
US20200095880A1 (en) * | 2018-09-24 | 2020-03-26 | United Technologies Corporation | Featherseal formed of cmc materials |
EP3819278A1 (en) * | 2019-11-11 | 2021-05-12 | Raytheon Technologies Corporation | Ceramic matrix composite-based seal |
US20220324206A1 (en) * | 2016-07-01 | 2022-10-13 | General Electric Company | Ceramic matrix composite articles having different localized properties and methods for forming same |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP6554882B2 (en) | 2015-04-07 | 2019-08-07 | 株式会社Ihi | Shield member and jet engine using the same |
US9759079B2 (en) | 2015-05-28 | 2017-09-12 | Rolls-Royce Corporation | Split line flow path seals |
US10718226B2 (en) | 2017-11-21 | 2020-07-21 | Rolls-Royce Corporation | Ceramic matrix composite component assembly and seal |
US11078802B2 (en) | 2019-05-10 | 2021-08-03 | Rolls-Royce Plc | Turbine engine assembly with ceramic matrix composite components and end face seals |
FR3100560B1 (en) * | 2019-09-06 | 2022-04-29 | Safran Aircraft Engines | Set for a turbomachine turbine |
US11041399B2 (en) | 2019-11-01 | 2021-06-22 | Raytheon Technologies Corporation | CMC heat shield |
FR3115811B1 (en) * | 2020-10-30 | 2023-02-24 | Safran Ceram | Assembly for turbine comprising sectors with laminated sealing tabs |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050186878A1 (en) * | 2004-02-23 | 2005-08-25 | General Electric Company | Thermo-mechanical property enhancement plies for CVI/SiC ceramic matrix composite laminates |
US7387758B2 (en) * | 2005-02-16 | 2008-06-17 | Siemens Power Generation, Inc. | Tabbed ceramic article for improved interlaminar strength |
US20100074729A1 (en) * | 2008-09-22 | 2010-03-25 | Siemens Energy, Inc. | Compressible Ceramic Seal |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4989886A (en) | 1988-12-30 | 1991-02-05 | Textron Inc. | Braided filamentary sealing element |
US5358262A (en) | 1992-10-09 | 1994-10-25 | Rolls-Royce, Inc. | Multi-layer seal member |
US5304031A (en) | 1993-02-25 | 1994-04-19 | The United States Of America As Represented By The Secretary Of The Air Force | Outer air seal for a gas turbine engine |
US5615893A (en) | 1996-01-16 | 1997-04-01 | Power Packing Company, Inc. | Split face mechanical sealing rings and their use |
GB9827889D0 (en) | 1998-12-18 | 2000-03-29 | Rolls Royce Plc | A method of manufacturing a ceramic matrix composite |
JP2000271736A (en) | 1999-03-29 | 2000-10-03 | Taiheiyo Cement Corp | Method for joining metal-ceramics composite material |
DE20311346U1 (en) | 2003-07-23 | 2003-10-02 | Burgmann Dichtungswerke Gmbh | For a common rotation with an engine shaft designed sliding ring of a mechanical seal arrangement for jet engines |
US20100327535A1 (en) | 2004-03-16 | 2010-12-30 | General Electric Company | Fiber seal for ceramic matrix composite components |
US7497443B1 (en) | 2005-05-03 | 2009-03-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Resilient flexible pressure-activated seal |
US7802799B1 (en) | 2006-09-18 | 2010-09-28 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of joining metallic and composite components |
US7870738B2 (en) | 2006-09-29 | 2011-01-18 | Siemens Energy, Inc. | Gas turbine: seal between adjacent can annular combustors |
US7771159B2 (en) | 2006-10-16 | 2010-08-10 | General Electric Company | High temperature seals and high temperature sealing systems |
US7798769B2 (en) | 2007-02-15 | 2010-09-21 | Siemens Energy, Inc. | Flexible, high-temperature ceramic seal element |
FR2913718B1 (en) | 2007-03-15 | 2009-06-05 | Snecma Propulsion Solide Sa | TURBINE RING ASSEMBLY FOR GAS TURBINE |
US8974891B2 (en) | 2007-10-26 | 2015-03-10 | Coi Ceramics, Inc. | Thermal protection systems comprising flexible regions of inter-bonded lamina of ceramic matrix composite material and methods of forming the same |
KR101512379B1 (en) | 2008-07-01 | 2015-04-16 | 삼성전자 주식회사 | Integrated circuit device for processing signal and image processing apparatus having the same |
EP2213841B1 (en) | 2009-01-28 | 2011-12-14 | Alstom Technology Ltd | Strip seal and method for designing a strip seal |
US8293356B2 (en) | 2009-05-12 | 2012-10-23 | Siemens Energy, Inc. | Subsurface inclusions of objects for increasing interlaminar shear strength of a ceramic matrix composite structure |
US8629592B2 (en) | 2009-06-25 | 2014-01-14 | General Electric Company | Hermetic sealing assembly and electrical device including the same |
US8359865B2 (en) | 2010-02-04 | 2013-01-29 | United Technologies Corporation | Combustor liner segment seal member |
US8359866B2 (en) | 2010-02-04 | 2013-01-29 | United Technologies Corporation | Combustor liner segment seal member |
JP5691409B2 (en) | 2010-11-01 | 2015-04-01 | イビデン株式会社 | C / C composite material and method for producing C / C composite material |
-
2013
- 2013-12-26 US US14/140,663 patent/US9757920B2/en not_active Expired - Fee Related
-
2014
- 2014-03-10 WO PCT/US2014/022387 patent/WO2014150147A1/en active Application Filing
- 2014-03-10 EP EP14716670.6A patent/EP2969554B1/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050186878A1 (en) * | 2004-02-23 | 2005-08-25 | General Electric Company | Thermo-mechanical property enhancement plies for CVI/SiC ceramic matrix composite laminates |
US7387758B2 (en) * | 2005-02-16 | 2008-06-17 | Siemens Power Generation, Inc. | Tabbed ceramic article for improved interlaminar strength |
US20100074729A1 (en) * | 2008-09-22 | 2010-03-25 | Siemens Energy, Inc. | Compressible Ceramic Seal |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9464535B2 (en) | 2013-05-27 | 2016-10-11 | Kabushiki Kaisha Toshiba | Stationary part sealing structure |
EP3061603A1 (en) * | 2015-02-27 | 2016-08-31 | General Electric Company | Cmc laminate structure fabricated using chemical vapor infiltration (cvi) |
US20170306779A1 (en) * | 2016-04-25 | 2017-10-26 | United Technologies Corporation | Creep resistant axial ring seal |
US10408074B2 (en) * | 2016-04-25 | 2019-09-10 | United Technologies Corporation | Creep resistant axial ring seal |
US20220324206A1 (en) * | 2016-07-01 | 2022-10-13 | General Electric Company | Ceramic matrix composite articles having different localized properties and methods for forming same |
US11890836B2 (en) * | 2016-07-01 | 2024-02-06 | General Electric Company | Ceramic matrix composite articles having different localized properties and methods for forming same |
US20180266261A1 (en) * | 2017-02-27 | 2018-09-20 | Rolls-Royce North American Technologies Inc. | Ceramic seal component for gas turbine engine and process of making the same |
US11255206B2 (en) | 2017-02-27 | 2022-02-22 | Rolls-Royce North American Technologies Inc. | Ceramic seal component for gas turbine engine and process of making the same |
US10794205B2 (en) * | 2017-02-27 | 2020-10-06 | Rolls-Royce North American Technologies Inc. | Ceramic seal component for gas turbine engine and process of making the same |
US20200095880A1 (en) * | 2018-09-24 | 2020-03-26 | United Technologies Corporation | Featherseal formed of cmc materials |
EP3819278A1 (en) * | 2019-11-11 | 2021-05-12 | Raytheon Technologies Corporation | Ceramic matrix composite-based seal |
US11519282B2 (en) * | 2019-11-11 | 2022-12-06 | Raytheon Technologies Corporation | Ceramic matrix composite-based seal |
US11920477B2 (en) | 2019-11-11 | 2024-03-05 | Rtx Corporation | Ceramic matrix composite-based seal |
Also Published As
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US9757920B2 (en) | 2017-09-12 |
EP2969554A1 (en) | 2016-01-20 |
EP2969554B1 (en) | 2019-05-08 |
WO2014150147A1 (en) | 2014-09-25 |
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